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Experimental evaluation of a translating nozzle sidewall radial turbineAn experimental performance evaluation was made of two movable sidewall variable area radial turbines. The turbine designs were representative of the gas generator turbine of a variable flow capacity rotorcraft engine. The first turbine was an uncooled design while the second turbine had a cooled nozzle but an uncooled rotor. The cooled nozzle turbine was evaluated both with and without coolant flow. The test results showed that the movable nozzle wall is a viable and efficient means to effectively control the flow capacity of a radial turbine. Peak efficiencies of the second turbine with and without nozzle coolant were 86.5 and 88 percent respectively. These values are comparable to pivoting vane variable geometry turbines; however, the decrease in efficiency as the flow was varied from the design value was much less for the movable wall turbine. Several design improvements which should increase the turbine efficiency one or two more points are identified. These design improvements include reduced leakage losses and relocation of the vane coolant ejection holes to reduce mainstream disturbance.
Document ID
19880008272
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Roelke, Richard J.
(NASA Lewis Research Center Cleveland, OH., Canada)
Rogo, Casimir
(Teledyne CAE Toledo, Ohio., United States)
Date Acquired
September 5, 2013
Publication Date
September 1, 1987
Publication Information
Publication: AGARD Advanced Technology for Aero Gas Turbine Components
Subject Category
Aircraft Propulsion And Power
Accession Number
88N17656
Distribution Limits
Public
Copyright
Other
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